Motor and decelerator integrated device applied to electric driven helicopter tail rotor and control method thereof

Abstract

The invention discloses a motor and decelerator integrated device applied to an electric driven helicopter tail rotor and a control method thereof. The integrated device comprises: a disc axial permanent magnet synchronous motor, a primary decelerator, and a controller. The disc axial permanent magnet synchronous motor is a coreless hollow structure of an outer rotor and an inner stator, and includes: a shell, a copper coil winding, an outer rotor permanent magnet, a rotor support frame, and a power transmission connecting rod. The primary decelerator is disposed in the inner stator structure, and includes: a small gear, a big gear, a big gear rear cover, an output shaft, and an angular contact ball bearing. The controller includes a rotor position sensor and a motor speed controller. The integrated device provided by the invention can save the internal space of the electric helicopter, shorten the output shaft distance and reduce the output shaft number so as to reduce the weight of the whole structure, thereby providing powerful guarantee for electric helicopter's longer time and longer distance flight.

Description

technical field [0001] The invention belongs to the field of aircraft design, and in particular relates to the field of design, manufacture and control of an electrically driven helicopter tail rotor transmission system for military or civilian use. Background technique [0002] The transmission system of the existing helicopter tail rotor is a separate type of motor and reducer, such as Figure 7 As shown, the driving mode is mostly fuel-driven. Although it is a commonly used transmission system structure on the market at present, and its technology and manufacture are relatively mature, but because it is spliced ​​by a large number of shafts, couplings and other structures, it has its own structural weight, large energy loss, and space occupation. Inherent shortcomings such as large size and difficult assembly and maintenance. [0003] However, if the planetary gear reducer is used in the reducer part of the integrated device of the motor and the reducer, such as Figure...

AI Technical Summary

Problems solved by technology

Although it is a commonly used transmission system structure on the market at present, and its technology and manufacture are relatively mature, but because it is spliced ​​by a large number of shafts, couplings and other structures, it has its own structural weight, large energy loss, and space occupation. Inherent shortcomings such as large size and difficult assembly and maintenance

[0003] However, if the planetary gear reducer is used in the reducer part of the integrated device of the motor and the reducer, such as Figure 8 As shown, although its structure has the characteristics of coaxial input and coaxial output, its structure alone has many gears and complex structure, resulting in excessive overall weight

And if the reducer part adopts the first-stage cylindrical gear external meshing method, such as Figure 9 As shown, it takes up more installation space, resulting in the overall available space is too small,

[0004] Since today's aircraft mostly use hybrid power, the control method design in the prior art is too simple, and it is difficult to cope with sudden changes in external conditions.

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